WO2013001091A1 - Système de joint d'étanchéité pour turbine à gaz - Google Patents

Système de joint d'étanchéité pour turbine à gaz Download PDF

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Publication number
WO2013001091A1
WO2013001091A1 PCT/EP2012/062818 EP2012062818W WO2013001091A1 WO 2013001091 A1 WO2013001091 A1 WO 2013001091A1 EP 2012062818 W EP2012062818 W EP 2012062818W WO 2013001091 A1 WO2013001091 A1 WO 2013001091A1
Authority
WO
WIPO (PCT)
Prior art keywords
coating
seal system
heat shield
abradable
thermal barrier
Prior art date
Application number
PCT/EP2012/062818
Other languages
English (en)
Inventor
Xin-hai LI
Peter Carlsson
Original Assignee
Siemens Aktiengesellschaft
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2013001091A1 publication Critical patent/WO2013001091A1/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/95—Preventing corrosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F05D2300/2118—Zirconium oxides
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

Definitions

  • Seal system for a gas turbine which seal system comprises a rotor blade tip with an abrasive coating system and a stationary heat shield ring coated with an abradable coating and facing opposite to the tip .
  • Shroudless gas turbine blades are increasingly used in gas turbines.
  • These dam- ages increase the gap between the blade tips and the heat shield segments continuously, leading to an increased hot gas leakage thereby reducing the efficiency of the gas turbine.
  • EP 0 707 091 Al describes a sealing system of gas turbines comprising a blade tip coated with a zirconium-based oxide having a plurality of vertical macrocracks .
  • the zirconium- based oxide with the macrocracks shows good rub tolerance when contacting a seal ring of bare superalloy.
  • the zirco ⁇ nium-based coating of EP 0 707 091 Al is a zirconia coating with macrocracks where the zirconia is partially stabilized, by an amount of 6.5 to 9 weight percent yttria.
  • An inventive seal system for a gas turbine comprises a rotor blade tip with an abrasive coating system and a stationary heat shield ring located opposite to the blade tip.
  • the heat shield ring may be formed by a number of ring segments together forming the seal ring.
  • the abrasive coating system on the blade tip comprises an oxidation resistant and/or corrosion resistant bond coat and a thermal barrier coating atop of the bond coat.
  • the thermal barrier coating is a Zr02 coating that is partially stabi ⁇ lized by Y2O 3 (abbreviated YSZ) and is free of macrocracks, at least of vertical macrocracks.
  • the heart shield ring is coated with an abradable coating.
  • the abrad- able coating may be a ceramic coating, for example a YSZ coating i.e., a coating of yttria stabilized zirconium oxide.
  • a crack is consid ⁇ ered to be a macrocrack if its lengh is at least 0,1 mm.
  • the thermal bar ⁇ rier coating of the blade tip may be fully rubbed off. How- ever, the oxidation resistant and/or corrosion resistant bond coat is still present to protect the tip.
  • the clearance be ⁇ tween the blade tip and the seal ring is small enough to pro ⁇ vide a good sealing action. In that sense, the thermal bar- rier coating can be regarded as sacrificial coating on top of the bond coat.
  • the thermal barrier coating without macrocracks of the seal system is preferably a Zr02 coating that is partially stabi ⁇ lized by 5 to 9 wt% Y2O 3 , in particular by 7 wt% Y2O 3 . More ⁇ over, the thermal barrier coating may be applied by air plasma spraying (APS) or by electron beam physical vapour deposition (EB-PVD) .
  • APS air plasma spraying
  • EB-PVD electron beam physical vapour deposition
  • the abrasive coating system i.e. the bond coat and the ther ⁇ mal barrier coating, may be particularly applied only on the tip region of the blade, or it may be applied as an extension from the coating system of the airfoil, or as an extension from the coating system of the airfoil and the platform.
  • Coating also other regions of the blade than the tip region with the abrasive coating system allows to coat the turbine blade in a single coating process.
  • the abrasive coating sys ⁇ tem is not subject to rubbing except for the tip region so that the thermal barrier coating will not be rubbed off in the other regions of the blade.
  • the thermal bar ⁇ rier coating has a porosity of more than 10% by volume. This measure helps to prevent the formation of macrocracks in the thermal barrier coating during applying the coating.
  • a suitable bond coat for the abrasive coating system is a so called MCrAlY-coating where M stands for cobalt (Co) , nickel (Ni) , or both of them, Cr stands for chromium, Al stands for aluminium and Y stands for yttrium and/or silicon (Si) and/or Hafnium (Hf) and/or at least one rare earth element.
  • M stands for cobalt (Co) , nickel (Ni) , or both of them
  • Cr stands for chromium
  • Al stands for aluminium
  • Y stands for yttrium and/or silicon (Si) and/or Hafnium (Hf) and/or at least one rare earth element.
  • a gas turbine comprising a rotor with one or more stages of rotor blades, a heat shield encasing at least one stage of rotor blades and an inventive seal system.
  • the heat shield segments are coated with the abradable coating to form the seal ring.
  • the tips of the rotor blades encased by the heat shield segments are coated with the abrasive coating system.
  • at least the first stage of rotor blades would be fitted with the seal system.
  • further stages, in particular the second stage can also be fitted with the seal system.
  • the inventive gas turbine has only small leakage so that high ef ⁇ ficiency of the gas turbine can be assured.
  • blade tip damages due to oxidation and/or corrosion can be reduced.
  • any ceramic coating being part of said abradable coating applied to said heat shield ring is free of vertical macrocracks . It is further preferred that any ceramic coating on top of said bond coat of said abrasive coating system of said blade tip is free of vertical macrocracks.
  • Figure 1 schematically shows an inventive seal system.
  • Figure 2 shows the seal system of figure 1 after start of a gas turbine engine of which it is part.
  • Figure 3 shows the seal system of figure 1 after a while of full engine load operation.
  • the seal system is part of a gas turbine with a rotor comprising a number of stages of turbine rotor blades arranged in axial direction of the rotor in alternating fashion with turbine nozzles.
  • the stages of rotor blades are encased by annular heat shields composed of a number of heat shield segments.
  • a stationary gas turbine has two to four stages of rotor blades and a corre ⁇ sponding number of vanes.
  • a turbine may also have only one stage of turbine blades or even more than four stages.
  • the gas turbine is equipped with an inventive seal system that comprises the tips of at least one of the stages of rotor blades and the respective heat shield.
  • Figure 1 schematically shows a heat shield segment 1 and a rotor blade 3.
  • the heat shield segment 1 is coated with an abradable coating 5 and represents a seal ring.
  • the abradable coating is preferably a yttria stabilized zirconiumoxide coating (YSZ) .
  • YSZ yttria stabilized zirconiumoxide coating
  • an abrasive coating system is present that comprises an oxidation resistant and/or cor ⁇ rosion resistant bond coat 9 and an overlying thermal barrier coating 11 that forms the top coat of the abrasive coating system.
  • a MCrAlY-coating is used as a bond coat 9, where M stands for iron, cobalt and/or nickel, Cr stands for chromium, Al stands for aluminium and Y stands for yttrium, hafnium, silicon or at least one rare earth element, or a combination thereof.
  • the top coat of the abrasive coat ⁇ ing system is, in present embodiment, zirconium oxide (Zr02) that is partially stabilized by 6 wt% yttrium oxide (Y 2 O 3 ) .
  • the spraying parameters are used to avoid the formation of macro- cracks, in particular the formation of vertical macrocracks.
  • the parameters when applying the YSZ-coating by air plasma spraying, are chosen such that only cracks oc- cure that are shorter than 0.1 mm.
  • Typical parameters that can be varied to achieve a macrocrack-free coating are tem ⁇ perature and velocity of the particles used in the spray process. Avoiding macrocracks can, for example, be achieved by setting the parameters in the air plasma spray process such that the applied YSZ-coating has a porosity larger that 10 % by volume. In this case, the formation of macrocracks is typically prevented.
  • the coating system may be an extension of the coating system applied on the whole airfoil 13 and the platform 15 of the rotor blade 3 which are exposed to hot combustion gases during gas turbine operation.
  • Figure 1 shows the inventive seal system formed by the seal ring 1 with the abradable coating 5 and the blade tip 7 with the abrasive coating system composted of the MCrAlY-bond coat 9 and the YSZ-top coat 11 just after applying it.
  • Figure 2 shows the seal system after start of the gas tur ⁇ bine.
  • the rotor blades 3 are arranged with a tiny gap between the tips 7 of the rotor blades 3 and the en ⁇ casing seal rings 1.
  • the gap between the surface of the top coat 11 and the surface of the abradable coating 5 is exaggerated for clarity reasons.
  • Dur ⁇ ing start up operation of the gas turbine an elongation of the turbine blades 3 occurs due to thermal expansion and cen ⁇ trifugal forces experienced by the blades 3 due to the rota- tion of the rotor.
  • the ceramic top coat 11 may be fully disappeared due to rubbing and due to lifetime limiting effects by bond coat oxidation in combination with thermal fatigue leading to spallation.
  • the sealing is still ensured and the bond coat 9 will not be rubbed off due to a space 17 that has been generated by the ceramic top coat 11 abrading into the abradable coating 5.
  • the bond coat 9 will still pro ⁇ tect the blade tip 7 from high temperature oxidation and/or corrosion for the rest of the operation time.
  • the YSZ-coating on the blade tip 7 provides a better abrad- ability at the high temperatures together with an abradable coating than a bare blade tip does. Moreover, the coated blade tip withstands a high temperature exposure up to 1200°C, and is even protected from oxidation and/or corrosion damages.
  • the YSZ-layer 11 of the abrasive coating system may be fully rubbed off by abrading to the abradable coating of the seal ring or by spallation when it reaches its lifetime during gas turbine operation within an overhaul in ⁇ terval, the YSZ has already rubbed into the abradable coating with a maximum depth after a short time of full-load opera ⁇ tion and, hence, fulfilled its function.
  • the YSZ-coating could be regarded as a sacrificial coating.
  • the removal of the YSZ-coating has left a space between the bond coat surface and the rubbed surface of the abradable coating 5, so that the bond coat 9 will not or minimally be rubbed off in the later operation and can still protect the blade tip 7 from the oxidation.
  • the invention has been described with respect to an exemplary embodiment thereof as an illustrative example of the inven- tive seal system and the inventive gas turbine.
  • a special embodiment has been de ⁇ scribed to explain the invention deviations from this embodi ⁇ ment are possible.
  • the zirconium oxide was stabilized by 7 wt% yttrium oxide in the described em- bodiment the contend of yttrium oxide may vary between 5 wt% and 9 wt%.
  • an MCrAlY-coating has been described as bond coat other oxidation and/or corrosion resistant bond coats, in particular other alumina scale forming bond coats, may be used.
  • the scope of the invention shall not be limited by the described exemplary embodiment but only by the appended claims.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Inorganic Chemistry (AREA)
  • Materials Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)

Abstract

L'invention concerne un système de joint d'étanchéité, pouvant s'user par frottement, pour une turbine à gaz, qui comprend une extrémité (7) de la pale de rotor avec un système de revêtement abrasif (9, 11) et un anneau stationnaire (1) de bouclier thermique faisant face à l'extrémité (7) de la pale et recouvert d'un revêtement pouvant s'user par frottement. Le système de revêtement abrasif comprend une couche d'accrochage (9) résistante à l'oxydation et/ou à la corrosion et un revêtement de barrière thermique (11) par-dessus la couche d'accrochage (9). Le revêtement de barrière thermique (11) est un revêtement en ZrO2 qui est partiellement stabilisé par du Y2O3 et exempt de macrofissures verticales.
PCT/EP2012/062818 2011-06-30 2012-07-02 Système de joint d'étanchéité pour turbine à gaz WO2013001091A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP11172105A EP2540973A1 (fr) 2011-06-30 2011-06-30 Système d'étanchéité pour turbine à gaz
EP11172105.6 2011-06-30

Publications (1)

Publication Number Publication Date
WO2013001091A1 true WO2013001091A1 (fr) 2013-01-03

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2012/062818 WO2013001091A1 (fr) 2011-06-30 2012-07-02 Système de joint d'étanchéité pour turbine à gaz

Country Status (2)

Country Link
EP (1) EP2540973A1 (fr)
WO (1) WO2013001091A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9316110B2 (en) 2013-08-08 2016-04-19 Solar Turbines Incorporated High porosity abradable coating

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2951400B1 (fr) 2013-01-29 2018-11-07 United Technologies Corporation Segment de matériau de frottement pour pales de rotor, turbine comprenant un segment de matériau de frottement, et utilisation d'une matrice de polymère comprenant des nanotubes de carbone comme matériau de frottement dans une turbine.
US10301949B2 (en) 2013-01-29 2019-05-28 United Technologies Corporation Blade rub material
EP2784268A1 (fr) 2013-03-28 2014-10-01 MTU Aero Engines GmbH Etanchéité extérieur d'une aube de turbine comprenant un revêtement ceramique sur le stator et le rotor respectivement
US10408224B2 (en) * 2014-01-23 2019-09-10 United Technologies Corporation Fan blades with abrasive tips
DE102018214752A1 (de) * 2018-08-30 2020-03-05 Siemens Aktiengesellschaft Verfahren zum Betrieb einer Gasturbine
US11566531B2 (en) * 2020-10-07 2023-01-31 Rolls-Royce Corporation CMAS-resistant abradable coatings

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0707091A1 (fr) 1994-09-16 1996-04-17 Praxair S.T. Technology, Inc. Aubes avec des potines à base de zircone possédant une structure macrofissurée et son procédé de production
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